Rotor shroud assembly
US5330321A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | May 11, 1993 |
| Grant date | Jul 19, 1994 |
| Priority date | — |
| Expiry date | May 11, 2013 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D11/18
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a gas turbine engine tip clearance between rotor blades and an encircling shroud liner is controlled by moving the shroud liner radially to match the thermal and centrifugal growth of the rotor assembly. The shroud liner segments are suspended between two axially displaced control rings located in a passageway carrying air ducted from the compressor. One control ring responds very quickly to changes in gas temperature corresponding to centrifugal growth and blade thermal growth. The other ring responds very much more slowly and corresponds to the thermal growth of the disc. The shroud liner segments are suspended from the control rings to adopt a position that constitutes the average between the growth positions of the two control rings.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.